General Electric Company

Ajay Gangadhar Patil

Brad Wilson Vantassel

William Scott Zemitis

Stephen Paul Wassynger

Melbourne James Myers

Jacob Charles Perry, Ii

Richard Ryan Pilson

Anthony Constantine Thermos

Rohit Pruthi

Martin James Jasper

Carlos Alberto Collado

Pradeep Jagannath Ghute

Debdulal Das

Michael Todd Summers

Karol Filip Leszczynski

Sanjay Shankar Jadhav

Shruti Kulkarni

Venkata Ramana Murthy Hemadribhotla

Siva Ram Surya Sanyasi Adavikolanu

Damian Wolff

Richa Singh

Cj Silver

A flow mixing lobe for an exhaust diffuser includes a first flange member having a first leading end, a first trailing end, and an intermediate portion extending therebetween. A second flange member includes a second leading end, a second trailing end, and an intermediate section extending therebetween. A first leg portion includes a first end extending from the first flange member, and a second end. A second leg portion has a first end portion extending from the second flange member, and a second end portion. A wing member is arranged between the first and second leg portions at respective ones of the second end and second end portions. The wing member includes a flow conditioning surface having a non-linear profile extending between the second end and the second end portion.

Manufacture and installation of diffuser flow mixing lobes

A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.

Edge profiles for tip shrouds of turbine rotor blades

Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.

Alignment apparatus for coupling diaphragms of turbines

According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud.

Turbine shroud engagement arrangement and method

A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating surface and a pressing member being more responsive to a high temperature condition associated with the flow of the working fluid than the vessel and being disposed within the recess to press the seal against the mating surface responsive to the condition being present.

Seal end attachment

An impingement plate is cooperable with a shroud assembly. The shroud assembly includes an outer shroud and plural inner shrouds with seals between the plural inner shrouds, respectively. The impingement plate includes a trailing edge portion, a leading edge portion and a mid portion between the trailing edge portion and the leading edge portion. A plurality of impingement holes are formed across an area of the impingement plate, and a cooling and damping section includes at least one channel that is shaped to accelerate cooling flow through the impingement plate.

Impingement plate for damping and cooling shroud assembly inter segment seals

Several physical features on an inlet guide vane (IGV) ensure proper orientation of the IGV within a compressor during assembly. A gear with several teeth removed results in a flat surface on the gear which inhibits the gear from rotating on the rack of the compressor inlet casing. An orientation pin is located in the internal bore of the gear. The cylindrical IGV spindle has a portion formed as a flat surface and the orientation pin engages this flat surface. These features are applicable to both a one-piece IGV where the jackshaft is integrated with the IGV stem and a two-piece IGV in which the jackshaft is separate from the IGV stem. A feature applicable to a two-piece IGV is a shaped boss on the IGV stem that allows the jackshaft to be located on the IGV stem in only one orientation.

Features to properly orient inlet guide vanes

Growing community of inventors

Greer, SC, United States of America

Ajay Gangadhar Patil